Aeroplane



A. T. ABRAM Y AEROPLANE Aug. 22, 1933.

4 sheets-'sheet 1' Filed Aug. 8, 1932 Inventor HZNJ ZT/'am A. T. ABRAM Aug. 22, 1933.

AEROPLANE 4 Sheets-Sheet 2 Filed Aug. 8. 1932 E, 6 2 l 2 MU lm w #o f o \IC fx. d o @f5 Z W 2 A al IJ 2 lo 2i 2 v q y By www* l .llorney Aug. 22, 1933. A r ABRAM 1,923,249

AEROPLANE Filed Aug. 8, 1932 4 Sheets-Sheet 3 Zai? Z4l "3'f"-\ /7 ---L+ Inventor 13g/wm@ Aug. 22, 1933. A1 ABRAM 1,923,249

AEROPLANE Filed Aug. 8, 1932 4 Sheets-Sheet 4 Inventor www/ih flliomey Patented Aug. 22, 1933 UNITED STATES PATENT OFFICE This invention relates broadly to aeroplanes and more particularly to control means therefor.` t

In accordance with the present invention 5 means is provided for use on an aircraft vto l Briefly the invention consists in the provision of airfoils of novel construction which maybe so arranged on an aeroplane and so manipulated for controlling the aeroplane as to enable the pilot to landthe aircraft at a relatively low speed within a restricted area; Y The invention also will be found to bea great aid toward the accomplishment of a properY take off of the aeroplane. -t v The invention together with its numerous ob- '20. jects and advantages will be best understood from the following descriptiom taken in connection with theaccompanying drawings wherein:

my airfoils mounted thereon.

Figure 2 is a side elevational view of an airfoil, one position of the same being suggested in full line vand the other in dotted line.

Figure 3 is a fragmentary top plan view of the airfoil the same being shown mounted on the aeroplane.

Figure 4 is a sectional view taken substantially on the line 4 4 of Figure 3.

Figure 5 is a sectional view taken substantially on the line 5 5 of Figure 2.

Figure 6 is a side elevational view of a slightly modified form of the invention. Y

Figure 7 is a top plan view of the form of the invention shown in Figure 6.

Figure 8 is a plan view of still another fo of the invention.

Figure 9 is a fragmentary plan view of yet another form of the invention.

Figure 10 is a transverse sectional view taken on the line 10'-10 of Figure 2.

With reference more in detail tothe drawings it will be seen that myv invention is applicable to a conventional type of aeroplane and in the present instance such an aeroplane is illustrated, the same including among other parts a fuselage 10 sustaining plane or wing 11, a propeller 12, and cam shaft 13 for driving the propeller 12. i

Reference being had to Figures 1 to 6 inclusive it will be seen that in this form of the in- Figure 1 is a plan view of anaeroplane having vention there is suitably mounted on the sustaining plane or wing ll a driven shaft 14 projecting at its end beyond the corresponding ends of the wing 11, and intermediate its ends geared to the shaft 13 as at 15. 60

Fixedly mountedY on each end of the sustaining ange or wing 11 is aY circular plate or disk 16, and each of the disks 16 is provided with a central aperture through which an end of the shaft 14 extends. On each end of 65 the shaft 14 is across head 17 that is provided at one end with a socket rotatably receiving the shank 18 of my improved airfoil designated generally 'by the reference character 19. The airfoil 19 is formed of lightweight of durable 70 material and is of the shape generally suggested in the drawings, being somewhat fan shaped as noted. 1

As shown in Figure 8 'the airfoil 19 is thickened as at 19a along its marginal edge and the 75 faces of the airfoil slope inwardly fromthe thickened vmarginal edge portion 19a toward the center of the airfoil. l

Fixed on the shank 18 of the'airfoil is a gear wheel 20, and the shank 18l is Vnormally held 80 against rotation relative to the cross head 17 through the medium of a spring pressed locking element or dog 21 pivotally mounted on the ,cross head 17 and having an end engageable with a selected one of a series of relatively spaced notches 22 provided on theV periphery of a'hub extension 23 of the gear 20.

. A disk or plate 16 is provided on the outer face vwith two Vdiametrically oppositeseries of teeth 24, and inwardly from the peripheral edge thereof` and in proximity to the teeth 24 with oppositely beveled cam lugs 25. y

On its free end cross head 17 is provided with a balancing weight 26, and the weight 26 as shown in Figure 5 is in cross section of air- 95 foil shape. From the description of the invention thus far it will be seen that when the shaft 13 drives propeller 12, shaft 14 will through the medium of the gearing 16 be driven inte the sheft'is thus causing the airfeus 19 te 100 rotate in a clockwise direction. As the gear 20 approaches eachA series of teeth 24 on the plate -16 `the' latch member 21 will first engage the cam 25 with the, result that substantially as soon as the gear 20 meshes with the referred 105 to series of teeth 24 the latch member 2l is rocked about its pivot, and moves out of engagement with a notch 22V whereupon the shank 18 will be free'to rotate. Manifestly as the shaft 14 is te rotate gear 2o meshes with 110 the aforementioned series of teeth 24 will cause the shank 18 to rotate thus'varying the angle or pitch of the airfoil 19. In this connection it is to be noted that the series of teeth 24 are so spaced relative to one another that the pitch of the airfoil 19 will be varied at substantially the completion of a half revolution of a cross head 17,l While the Yteeth 24 of each series are of such a number that the shank 1S of ythe air-- foil will only be rotated about yone quarter of a revolution. It will be also' further noted that the series of teeth 24 are so arranged that the pitch of the airfoil will be changed only when the cross headv 17 is at an angle to the perpendicular.

For controlling the transmission of power fromrthe shaft 14 to the shaft 15 there proor no resistance. Further the clutch 27 is released so that there is no transmissionrpower to the shaft 14. I je e Y For applying a braking action to the aircraft, as might be desired for slowingl the speed of the aircraft when landing, clutch 27 is thrown in whereby drive from shaft 13 is transmitted to shaft14-causing the cross heads 17 to rotate in a lclockwise direction. Obviously as the cross heads rotate in a clockwisedirection the gears will be brought into mesh with a series of teeth 24 on` each plate resulting, in a manner, above described, in a rotation of` the airfoils 19 so that the faces of the airfoil are disposed atzaV slight angle tothe line of flight thus serving to slightly retard the speed of the aeroplane.v As the shaft 14 continues to rotate the gears 20 pass into mesh with the second series of teeth 24 where-` upon the airfoils 19 are further rotated so that their faces are disposed at right angles tothe line of night, and the airfoils in this last named position obviously serveto further decreasethe speedof the aeroplane. Y

In the form of the invention shown in Figures 6 to v9 inclusive insteadof providing each Across e head with an airfoil and a balance weight each cross head is provided with two airfoils 19 arranged substantially rwith their faces at right angles to one another; Also each cross head 17' is provided Aat each end with a socket Vfor receivinga shank 18 of an airfoil. v Also each shank 18 'is provided with agear 20 for mesh with the teeth. of kthe series I24,'of teeth on anadjacent plate 16. Each gear 20' is also provided with a notched collar` or hub extension 23' `having notches 22 with which is engageable Ya pivoted latch member 21' provided l on an adjacent end of the cross head.

The form of the invention just described will be found especially useful for assisting the aeroplane lwhen taking off". In the form of the invention shownvin Figure' 7 the plates 16 areV mounted onthev shaft 14 for rotation relative thereto, and each plate is provided with a hub carrying a gear wheel` 29 with which pinions 30 are vin constant mesh.v

l the shaft 31, the;motion of the shaft 31'being transmitted to the plate 16' through the medium of the gearing 29, 30.

In this last named form of the invention plates 16 can be readily rotated in a clockwise direction a desired fraction of a revolution sufficient to so position the teeth on the plates that the gear wheels 20' will mesh with the teeth 24 when the cross heads 17 are in substantially horizontal position, with the result the airfoils 19 being in the position suggested in Figure 7 will materially assist in the forward propulsion of the aircraft, increasing the speed of the aircraft. j

In Figures 1 to 7 inclusive I have shown the shafts 14, 14 as extended longitudinally of the sustaining wing of the aeroplane for the full length of the sustaining wing. In Figure 8, I have shown afslightlymodifled form of sustaining Wing, the same being designated by the reference character 11. In this form of the invention ythe wingll'` at itsl leading edge and inwardly from the ends thereof, and in proxin Figure 8 being designated by the reference l character 14a is relativelyl shorter than shafts 14, Y14 with the result that the airfoils are disposed inwardly ak considerable distance from the end of the sustaining plane or wing. ,Y

In the form of the invention shown in Figure 9 the lprojection 11b vdoes notproject forwardly as far as the projection 11a in Figure 48 and to compensate forv lift, the sustaining wing 11" adjacent the projection 1lb is notched in Va suitable manner and as indicated at 32 so as not to interfere with the operation of the airfoil.

Even though I Ihave herein shown and described the preferred embodiment of the invention, it isV tobeunderstood that the same is susceptible of further changes, modifications and improvements coming within the scope of the 1 2. vIn an aeroplane, a laterallyrdisposed plate mounted on saidaeroplane, and provided with diametrically opposite series vof gear teeth, a member rotatable von an axis concentric to said plate, said member being also provided with a socket, an airfoilme'mber comprising arshank rotatably mounted in said socket, a broad `flat fan-shaped head on one end of said shank, a

gear on said'shank adapted 'to mesh withV each series of gear teeth forrotating said shank at predetermined'points 'in the rotation of said member, interengaging means on saidV shank and said member for normally retaining the shank against rotation, and means on said plate Afor releasing saidY interengaging means` each time said gear approaches a series of gear teeth on said plate. f

3. In an aeroplane, a plate provided adjacent its peripheral edge and on one face with an arcuate series of gear teeth, a member rotatable on an axis concentric to said plate, an airfoil rotatably mounted on said member, a gear on said airfoil adapted to mesh With said gear teeth for rotating said airfoil, interengaging means on said member and said airfoil for releasably retaining the airfoii against rotation relative to said member, and including a pivoted latch, and means on said plate for engaging said latch to release said inter-engaging means each time said airfoil approaches said gear teeth.

AUGUSTUS T. ABRAM. 

